Abstract: An assembly can include a chassis that includes a chamber and an opening; a cover movable for access to the chamber via the opening; a cover latch; and a cover latch release that includes a push panel operatively coupled via a linkage to a pull panel that includes a finger grip surface, where the linkage rotates the pull panel responsive to rotation of the push panel to expose the finger grip surface, and where further rotation of the pull panel releases the cover latch.

Abstract: An aircraft assembly having a titanium rod comprising a first threaded portion, and a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with it. One of the first and second threaded portions defines a male thread and the other one of the first and second threaded portions defines a female thread such that the nut can be wound in threading engagement along the rod. A threaded insert formed from a first metal of different hardness in comparison to titanium is coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first and second threaded portions is formed from titanium and the other one of the first and second threaded portions is formed from the first metal.

Abstract: A telescopic device having a housing and a rod is slidably mounted within a bore of the housing. First and second bearings provide sliding engagement between the rod and the housing. The first bearing is mounted relatively close to the open end of the bore and the second bearing is mounted relatively far from the open end of the bore relative to the first bearing. The second bearing is annular in shape with a central axis, the bearing has a radially outer mounting surface of arcuate cross-section and a radially inner bearing surface for sliding engagement with an outer surface of the rod and wherein the inner sidewall is provided with an annular groove having a second mounting surface of arcuate cross-section to house and retain the second bearing.

Abstract: A device can include a first housing that includes a first display and a first recess; a second housing that includes a second display and a second recess; and a retractable hinge assembly where, in a planar orientation of the first housing and the second housing, the retractable hinge assembly is retracted in part in the first recess and in part in the second recess.

Abstract: An aircraft assembly having a titanium rod comprising a first threaded portion, and a titanium nut comprising a second threaded portion conforming with the first threaded portion for mating engagement with it. One of the first and second threaded portions defines a male thread and the other one of the first and second threaded portions defines a female thread such that the nut can be wound in threading engagement along the rod. A threaded insert formed from a first metal of different hardness in comparison to titanium is coupled to the rod or the nut to define the first threaded portion or the second threaded portion respectively such that one of the first and second threaded portions is formed from titanium and the other one of the first and second threaded portions is formed from the first metal.

Abstract: A telescopic device having a housing and a rod is slidably mounted within a bore of the housing. First and second bearings provide sliding engagement between the rod and the housing. The first bearing is mounted relatively close to the open end of the bore and the second bearing is mounted relatively far from the open end of the bore relative to the first bearing. The second bearing is annular in shape with a central axis, the bearing has a radially outer mounting surface of arcuate cross-section and a radially inner bearing surface for sliding engagement with an outer surface of the rod and wherein the inner sidewall is provided with an annular groove having a second mounting surface of arcuate cross-section to house and retain the second bearing.

Abstract: A hydraulic actuator having a body defining a chamber, a piston rod including an annular groove and a piston head slidably housed within the chamber, the piston head having a number of segments each of which has a base portion mounted within the annular groove.

Abstract: An aircraft spring assembly includes a helical spring having a hollow core. A polymer damping member is confined within the core and is narrower than the internal spring diameter so as to be free to move along the core.

Abstract: An aircraft landing gear includes an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on the axle and arranged to define a brake rod connection point that is distinct from a conventional brake rod connection point defined by the brake assembly. The adaptor member is coupled to the brake assembly via an adaptor linkage that is arranged to react brake torque but arranged to permit relative movement between the adaptor member and the brake assembly in degrees of freedom which are not required to react brake torque.

Abstract: A hydraulic actuator having a body defining a chamber, a piston rod including an annular groove and a piston head slidably housed within the chamber, the piston head having a number of segments each of which has a base portion mounted within the annular groove.

Abstract: An aircraft spring assembly includes a helical spring having a hollow core. A polymer damping member is confined within the core and is narrower than the internal spring diameter so as to be free to move along the core.

Abstract: An aircraft landing gear includes an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on the axle and arranged to define a brake rod connection point that is distinct from a conventional brake rod connection point defined by the brake assembly. The adaptor member is coupled to the brake assembly via an adaptor linkage that is arranged to react brake torque but arranged to permit relative movement between the adaptor member and the brake assembly in degrees of freedom which are not required to react brake torque.

Abstract: A landing gear (10), including: a bogie beam (12); an axle (14) pivotally connected to the bogie beam (12); a locking member (40) coupled to the axle (14) such that movement of the axle (14) invokes movement of the locking member (40), said movement of the locking member (40) defining a swept volume; and a locking mechanism (60) coupled to the bogie beam (12) and including first (65a) and second glide members, (65a, 65b) the locking mechanism (60) being arranged to move the glide members (65a, 65b) between locking positions, where glide members (65a, 65b) are within the swept volume on opposing sides of the locking member (40) and in which position the locking mechanism (60) is arranged to lock the locking member (40) in a predetermined position, and non-locking positions, where the locking mechanism (60) is arranged permit movement of the locking member (40).

Abstract: An aircraft landing gear assembly includes a bogie beam, a landing gear strut and a stop. The landing gear strut has a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam. The stop is arranged to limit pivotal movement of the bogie beam relative to the landing gear strut The stop includes an elongate member arranged to be deflectable in bending when the bogie beam reaches a pivotal limit.

Abstract: A landing gear (10), including: a bogie beam (12); an axle (14) pivotally connected to the bogie beam (12); a locking member (40) coupled to the axle (14) such that movement of the axle (14) invokes movement of the locking member (40), said movement of the locking member (40) defining a swept volume; and a locking mechanism (60) coupled to the bogie beam (12) and including first (65a) and second glide members, (65a, 65b) the locking mechanism (60) being arranged to move the glide members (65a, 65b) between locking positions, where glide members (65a, 65b) are within the swept volume on opposing sides of the locking member (40) and in which position the locking mechanism (60) is arranged to lock the locking member (40) in a pre-determined position, and non-locking positions, where the locking mechanism (60) is arranged permit movement of the locking member (40).

Abstract: An aircraft landing gear assembly including a bogie beam, a landing gear strut having a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam, and a stop arranged to limit pivotal movement of the bogie beam relative to the landing gear strut, wherein the stop comprises at least one elongate member arranged to be deflectable in bending when the bogie beam reaches a pivotal limit.